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DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: DEFIANT CANARD BL110 AIRFOIL (defcnd2-il)
Reynolds number: 50,000
Max Cl/Cd: 28.27 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-defcnd2-il-50000-n5.txt
Download as CSV file: xf-defcnd2-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DEFIANT CANARD BL110 AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3083   0.10200   0.09558  -0.0497   1.0000   0.0577
  -9.500  -0.3164   0.09915   0.09285  -0.0492   1.0000   0.0568
  -9.250  -0.3287   0.09650   0.09033  -0.0482   1.0000   0.0559
  -9.000  -0.3451   0.09404   0.08800  -0.0468   1.0000   0.0550
  -8.750  -0.3653   0.09155   0.08563  -0.0454   1.0000   0.0542
  -8.500  -0.3899   0.08876   0.08296  -0.0444   1.0000   0.0534
  -8.250  -0.4130   0.08400   0.07827  -0.0472   0.9957   0.0521
  -8.000  -0.4458   0.07453   0.06837  -0.0554   0.9785   0.0491
  -7.750  -0.4382   0.06983   0.06350  -0.0582   0.9694   0.0488
  -7.500  -0.4345   0.06568   0.05914  -0.0595   0.9591   0.0486
  -7.250  -0.4287   0.06146   0.05460  -0.0606   0.9496   0.0485
  -7.000  -0.4192   0.05728   0.04998  -0.0617   0.9408   0.0489
  -6.750  -0.4112   0.05387   0.04621  -0.0613   0.9309   0.0496
  -6.500  -0.3864   0.05123   0.04346  -0.0630   0.9246   0.0514
  -6.250  -0.3737   0.04876   0.04070  -0.0621   0.9147   0.0524
  -6.000  -0.3494   0.04563   0.03709  -0.0631   0.9082   0.0532
  -5.500  -0.3039   0.04057   0.03115  -0.0628   0.8921   0.0550
  -5.250  -0.2810   0.03864   0.02880  -0.0622   0.8828   0.0566
  -5.000  -0.2463   0.03667   0.02624  -0.0632   0.8764   0.0603
  -4.750  -0.2194   0.03511   0.02462  -0.0633   0.8671   0.0634
  -4.500  -0.1853   0.03361   0.02294  -0.0641   0.8593   0.0670
  -4.250  -0.1504   0.03226   0.02131  -0.0647   0.8507   0.0718
  -4.000  -0.1207   0.03116   0.02020  -0.0647   0.8408   0.0798
  -3.750  -0.0828   0.02986   0.01878  -0.0660   0.8332   0.0915
  -3.500  -0.0588   0.02892   0.01782  -0.0650   0.8213   0.1087
  -3.250  -0.0335   0.02777   0.01682  -0.0645   0.8102   0.1473
  -3.000  -0.0087   0.02594   0.01576  -0.0642   0.8016   0.2657
  -2.750  -0.0045   0.02439   0.01563  -0.0595   0.7890   0.5060
  -2.500   0.0209   0.02418   0.01604  -0.0559   0.7785   0.7495
  -2.250   0.0829   0.02451   0.01612  -0.0584   0.7723   0.8580
  -2.000   0.1681   0.02498   0.01611  -0.0667   0.7642   0.9140
  -1.750   0.2553   0.02490   0.01553  -0.0765   0.7572   0.9513
  -1.500   0.3151   0.02467   0.01498  -0.0828   0.7456   0.9725
  -1.250   0.3644   0.02435   0.01439  -0.0873   0.7340   0.9874
  -1.000   0.4102   0.02399   0.01376  -0.0913   0.7227   0.9995
  -0.750   0.4279   0.02389   0.01350  -0.0899   0.7109   1.0000
  -0.500   0.4409   0.02392   0.01340  -0.0878   0.6980   1.0000
  -0.250   0.4544   0.02395   0.01331  -0.0858   0.6856   1.0000
   0.000   0.4690   0.02397   0.01320  -0.0838   0.6742   1.0000
   0.250   0.4868   0.02390   0.01298  -0.0822   0.6645   1.0000
   0.500   0.5010   0.02398   0.01294  -0.0801   0.6533   1.0000
   0.750   0.5146   0.02412   0.01297  -0.0780   0.6423   1.0000
   1.000   0.5321   0.02417   0.01288  -0.0763   0.6329   1.0000
   1.250   0.5491   0.02427   0.01285  -0.0745   0.6231   1.0000
   1.500   0.5632   0.02451   0.01299  -0.0724   0.6127   1.0000
   1.750   0.5831   0.02459   0.01293  -0.0710   0.6039   1.0000
   2.000   0.5995   0.02484   0.01308  -0.0691   0.5943   1.0000
   2.250   0.6161   0.02515   0.01329  -0.0674   0.5852   1.0000
   2.500   0.6380   0.02533   0.01335  -0.0664   0.5776   1.0000
   2.750   0.6528   0.02579   0.01375  -0.0644   0.5685   1.0000
   3.000   0.6781   0.02589   0.01370  -0.0638   0.5614   1.0000
   3.250   0.6911   0.02642   0.01421  -0.0616   0.5515   1.0000
   3.500   0.7128   0.02666   0.01434  -0.0605   0.5434   1.0000
   3.750   0.7305   0.02705   0.01466  -0.0589   0.5343   1.0000
   4.000   0.7482   0.02748   0.01504  -0.0573   0.5261   1.0000
   4.250   0.7682   0.02787   0.01538  -0.0561   0.5184   1.0000
   4.500   0.7857   0.02842   0.01591  -0.0546   0.5115   1.0000
   4.750   0.8020   0.02905   0.01655  -0.0531   0.5047   1.0000
   5.000   0.8293   0.02934   0.01679  -0.0529   0.5000   1.0000
   5.250   0.8351   0.03041   0.01796  -0.0501   0.4928   1.0000
   5.500   0.8563   0.03093   0.01848  -0.0493   0.4874   1.0000
   5.750   0.8735   0.03164   0.01921  -0.0479   0.4819   1.0000
   6.000   0.8828   0.03264   0.02029  -0.0457   0.4755   1.0000
   6.250   0.9079   0.03303   0.02071  -0.0453   0.4708   1.0000
   6.500   0.9130   0.03427   0.02205  -0.0426   0.4646   1.0000
   6.750   0.9252   0.03522   0.02308  -0.0408   0.4590   1.0000
   7.000   0.9525   0.03560   0.02347  -0.0408   0.4552   1.0000
   7.250   0.9438   0.03754   0.02558  -0.0369   0.4488   1.0000
   7.500   0.9535   0.03872   0.02684  -0.0350   0.4438   1.0000
   7.750   0.9812   0.03913   0.02730  -0.0350   0.4404   1.0000
   8.000   0.9475   0.04234   0.03063  -0.0288   0.4332   1.0000
   8.250   0.9530   0.04389   0.03226  -0.0269   0.4284   1.0000
   8.500   0.9827   0.04420   0.03265  -0.0271   0.4255   1.0000
   8.750   0.9148   0.05092   0.03943  -0.0213   0.4147   1.0000
   9.000   0.9402   0.05127   0.03990  -0.0209   0.4117   1.0000
   9.500   0.8978   0.06076   0.04949  -0.0184   0.3969   1.0000
  10.250   0.8220   0.07974   0.06862  -0.0195   0.3741   1.0000
  10.500   0.8265   0.08261   0.07156  -0.0195   0.3700   1.0000
  10.750   0.8473   0.08347   0.07257  -0.0190   0.3672   1.0000
  11.000   0.8220   0.08960   0.07873  -0.0198   0.3586   1.0000
  11.250   0.8362   0.09112   0.08036  -0.0195   0.3540   1.0000
  11.500   0.8630   0.09121   0.08059  -0.0188   0.3512   1.0000
  11.750   0.8338   0.09779   0.08721  -0.0199   0.3414   1.0000
  12.000   0.8550   0.09848   0.08804  -0.0194   0.3373   1.0000
  12.250   0.8421   0.10310   0.09276  -0.0201   0.3288   1.0000
  12.500   0.8579   0.10428   0.09406  -0.0197   0.3231   1.0000
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